US3688989A - Thrust reversers for aircraft - Google Patents

Thrust reversers for aircraft Download PDF

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Publication number
US3688989A
US3688989A US121512A US3688989DA US3688989A US 3688989 A US3688989 A US 3688989A US 121512 A US121512 A US 121512A US 3688989D A US3688989D A US 3688989DA US 3688989 A US3688989 A US 3688989A
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Prior art keywords
aircraft
thrust reverser
bucket
arm
point
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Expired - Lifetime
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US121512A
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English (en)
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David Roberts Mcmurtry
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    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/54—Nozzles having means for reversing jet thrust
    • F02K1/56—Reversing jet main flow
    • F02K1/60—Reversing jet main flow by blocking the rearward discharge by means of pivoted eyelids or clamshells, e.g. target-type reversers

Definitions

  • ABSTRACT A thrust reverser linkage in which two main arms are pivoted together at a point between their ends in the manner of a pair of scissors. One end of one arm is connected to a thrust reverser bucket the other end being connected to aircraft structure. One end of the second arm is connected via a pivoted link with a thrust reverser bucket and the other end being movable by an actuating mechanism.
  • the present invention relates to thrust reversers for aircraft, and in particular relates to an operating mechanism for a thrust reverser.
  • an aircraft is provided with at least one gas turbine jet propulsion engine mounted within aircraft structure, 'a thrust reverser comprising a pair of buckets which are movable from an inoperative position in which they form part of the aircraft structure to an operative position in which they lie in the path of the exhaust gases of the engine or engines, and an operating mechanism for each bucket of the thrust reverser, which mechanism comprises a pair of main arms pivoted together at a point between their ends, one end of one of the arms being directly pivotably connected to a first point on the thrust reverser bucket, one end of the second arm being connected to a second point on the thrust reverser bucket, spaced apart from the first point, by means of a pivotable extension link on said one end and means operable on one or both of the other ends of the arms to produce relative movement between said other ends to move the bucket between its operative and inoperative positions.
  • the said other end of one of the arms may be connected directly to theaircraft structure so that only one of the said other ends is movable.
  • aircraft structure is to be taken to include the fuselage of an aircraft, or a pod with which an engine may be mounted externally of the fuselage.
  • an aircraft is provided with at least one gas turbine jet propulsion engine mounted within aircraft structure, a thrust reverser comprising a pair of buckets which are movable from an inoperative position in which they form part of the aircraft structure to an operative position in which they lie in the path of the exhaust gases of the engine or engines, and an operating mechanism for each bucket of the thrust reverser, which mechanism comprises a pair of main arms pivoted together at a point between their ends, in the form of scissors, one end of a first one of the arms being pivotably anchored to aircraft structure, and the other end being pivotably connected at a first point on the thrust reverser bucket, one end of the second one of the arms being connected to the thrust reverser bucket at a point spaced apart from said first point through a pivotable extension link, the other end of the second arm being connected to a second link which is anchored to aircraft structure, means being provided which is operable to move said other end of the second arm towards the anchored end of the first arm.
  • the movable means comprises a
  • the further pivotable link may be anchored to aircraft structure at a point either above or below the said other end of the second arm
  • the further pivotable link, the second arm and the extension link on the second arm all lie in a straight line when the thrust reverser is in its operative position.
  • the actuator may be of any suitable type. Thus it may be a ram or jack, and may be hydraulically, pneumatically, electrically or mechanically operated. In the preferred embodiment the actuator takes the form of a jack operated by a lead screw rotated by an air motor.
  • FIG. 1 is a diagrammatic view of an aircraft according to the invention showing the thrust reversing buckets in the inoperative position
  • FIG. 2 shows half of the linkage in more detail with one of the buckets in the inoperative position
  • FIG. 3. shows the same linkage with the bucket in an intermediate position
  • FIG. 4 shows the same linkage with the bucket in the operative position.
  • FIG. 1 shows an external view of an aircraft, and indicates, in dotted lines, the position of one of a pair of jet propulsion engines 1 which lie side by side in the fuselage of the aircraft.
  • the engine 1 has the usual compressor means 2, combustion equipment 3, turbine means 4, and propulsion nozzle 5 all in flow series. 1
  • a thrust reverser is mounted from aircraft structure andconsists of a pair of buckets 11 movable from an inoperative position, in which the buckets are stowed out of the path of the exhaust gases of the engine, into an operative position in which the exhaust gases from the propulsion nozzle 5 impinge on the buckets and are deflected to provide reverse thrust.
  • the buckets 11 are dimensioned so as to form a smooth continuation of the fuselage 12 of the aircraft, in which the engine is mounted, when in their inoperative position.
  • the nozzle 5 projects beyond the end of the aircraft fuselage and the thrust reverser buckets must therefore be moved in such a manner that the initial movement of each bucket is radially outwards and rearwards in order not to foul the downstream ends of the fuselage and nozzle.
  • FIG. 2, 3 and 4 a linkage system which performs this type of movement is shown.
  • the linkage is basically a scissors type of linkage, the two main arms of the scissors being the arms 19 and 20 which are pivoted together at a main pivot 22.
  • One end of the arm 19 is connected to the thrust reverser bucket 11 at its upstream end by means of a pivotable connection 21, and the other end of the arm is earthed' to aircraft structure by means of a pivot 23, (i.e. pivot 23 is fixed on aircraft structure).
  • One end of the other arm 20 is connected to an extension link 24 which is connected to the downstream end of the thrust reverser bucket by a pivot at 25.
  • the other end of the arm 20 is connected to an extension link 26 which is earthed to the aircraft structure at 27 by means of a pivot.
  • An actuating means which comprises a screw jack 28 is provided and is connected by an actuating link 29 to a point on the link 26.
  • the links are arranged so that when the thrust reverser is in its inoperative position they retract into theaircraft fuselage into a minimum space which does not require a local enlargement of the fuselage of the aircraft. Additionally, with the thrust reverser in its operative position the links form straight lines between the buckets and the earth points on the aircraft fuselage, so that the links are in tension and there are no bending moments applied to any of the links or the screw jack.
  • FIG. 3 shows an intermediate position of the thrust reverser bucket'from which it can be seen that the two main arms 19 and 20 become substantially vertical while the link 24 has become horizontal.
  • the relative positions of the various links arms and pivots is determined by certain criteria based on design practice, together with a certain amount of trial and error to produce the linkage with the optimum size for a given'installation.
  • thelinks and arms should form straight lines between the earth points and the buckets to avoid introducing bending stresses into the linkage.
  • the actuating means in the above example is a jack 28 movable by means of a lead screw 30, driven by a motor (not shown) which may be hydraulically, pneumatically or electrically driven.
  • actuator Any other suitable form of actuator may be used for example, a hydraulic ram.
  • linkage shown in this example is merely illustrative of one type of linkage which suited the particular installation.
  • the scissor arms 19 and 20 may be connected to the bucket or to the aircraft structure or actuating mechanism by means of different arrangements of links and still provide the requisite movement.
  • anchor link 26 may be anchored at a point below pivot connection between link 26 and arm 20, resulting in a re-positioning of the point of actuation of the actuating jack 28.
  • a thrust reverser comprising a pair of buckets which are movable from an inoperative position in which they form part of the aircraft structure, to an operative position in which they lie in the path of the exhaust gases of the engine, and an operating mechanism for each bucket of the thrust reverser, which mechanism comprises a pair of main arms pivoted together at a point between their ends, one end of one of the arms being directly pivotably connected to a first point on the thrust reverser bucket, one end of the second arm being connected to a second point on the thrust reverser bucket, spaced apart from the first point, by means of a pivotable extension link on said one end, and means operable on one of the other ends of the arms to produce relative movement between said other ends to move the bucket between its operative and inoperative positions.
  • An aircraft provided with at least one gas turbine jet propulsion engine mounted within aircraft structure, a thrust reverser comprising a pair of buckets which are movable from an inoperative position in which they form part of the aircraft structure, to an operative position in which they lie in the path of the exhaust gases of the engine, and an operating mechanism for.
  • each bucket of the thrust reverser which mechanism comprises a 7 pair of main arms pivoted together at a point between their ends, in the form of scissors, one end of a first one of the arms being pivotably anchored to aircraft structure, and the other end being pivotably connected at a first point on the thrust reverser bucket, one end of the second one of the arms being connected to the thrust reverser bucket at a point spaced apart from said first point through a pivotable extension link, the other end of the second arm being connected to a second link which is anchored to aircraft structure, means being provided which is operable to move said other end of the second arm towards the'anchored end of the first arm.
  • operable means comprises a further pivotable link movable by means of an actuator to translate said second arm axially.

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  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Transmission Devices (AREA)
  • Control Of Turbines (AREA)
US121512A 1970-03-14 1971-03-05 Thrust reversers for aircraft Expired - Lifetime US3688989A (en)

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GB1235470 1970-03-14

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US3688989A true US3688989A (en) 1972-09-05

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US (1) US3688989A (fr)
FR (1) FR2081954B1 (fr)
GB (1) GB1288834A (fr)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3915415A (en) * 1974-03-21 1975-10-28 Rohr Industries Inc Overwing thrust reverser
US3981463A (en) * 1974-03-21 1976-09-21 Rohr Industries, Inc. Overwing thrust reverser
US4005836A (en) * 1975-12-22 1977-02-01 Rohr Industries, Inc. Target thrust reverser
USRE31591E (en) * 1975-03-27 1984-05-29 The Boeing Company Fuselage tail jet engine thrust reverser and method
US20110016846A1 (en) * 2007-08-20 2011-01-27 Aircelle Method and system for controlling at least one actuator of the cowlings of a turbojet engine thrust inverter

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
IT1257222B (it) * 1992-06-09 1996-01-10 Alenia Aeritalia & Selenia Dispositivo inversore di spinta per motori aeronautici a getto.
FR2722534B1 (fr) * 1994-07-13 1996-08-14 Hispano Suiza Sa Inverseur de poussee de turboreacteur double flux, a obstacles externes

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3164956A (en) * 1963-03-14 1965-01-12 Boeing Co Two part thrust reverser
US3610533A (en) * 1970-06-29 1971-10-05 Gen Electric Variable area and thrust-reversing nozzle

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB895872A (en) * 1959-11-19 1962-05-09 Rolls Royce Jet propulsion engines
FR1300774A (fr) * 1960-05-13 1962-08-10 Bristol Siddeley Engines Ltd Perfectionnements apportés aux installations de force motrice pour la propulsion des aéronefs

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3164956A (en) * 1963-03-14 1965-01-12 Boeing Co Two part thrust reverser
US3610533A (en) * 1970-06-29 1971-10-05 Gen Electric Variable area and thrust-reversing nozzle

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3915415A (en) * 1974-03-21 1975-10-28 Rohr Industries Inc Overwing thrust reverser
US3981463A (en) * 1974-03-21 1976-09-21 Rohr Industries, Inc. Overwing thrust reverser
USRE31591E (en) * 1975-03-27 1984-05-29 The Boeing Company Fuselage tail jet engine thrust reverser and method
US4005836A (en) * 1975-12-22 1977-02-01 Rohr Industries, Inc. Target thrust reverser
US20110016846A1 (en) * 2007-08-20 2011-01-27 Aircelle Method and system for controlling at least one actuator of the cowlings of a turbojet engine thrust inverter
US9448557B2 (en) * 2007-08-20 2016-09-20 Safran Nacelles Method and system for controlling at least one actuator of the cowlings of a turbojet engine thrust inverter

Also Published As

Publication number Publication date
DE2111994B2 (de) 1976-11-18
GB1288834A (fr) 1972-09-13
DE2111994A1 (de) 1971-10-07
FR2081954B1 (fr) 1975-03-21
FR2081954A1 (fr) 1971-12-10

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